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GOE 529 AIRFOIL (goe529-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 529 AIRFOIL (goe529-il)
Reynolds number: 500,000
Max Cl/Cd: 108.95 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe529-il-500000-n5.txt
Download as CSV file: xf-goe529-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 529 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2705   0.11782   0.11552  -0.0358   1.0000   0.0087
 -10.750  -0.2673   0.11471   0.11244  -0.0364   1.0000   0.0086
 -10.500  -0.2654   0.11136   0.10911  -0.0370   1.0000   0.0087
 -10.250  -0.2591   0.10702   0.10479  -0.0393   0.9919   0.0089
 -10.000  -0.2528   0.10142   0.09919  -0.0432   0.9826   0.0093
  -9.750  -0.2416   0.09638   0.09414  -0.0478   0.9715   0.0095
  -9.500  -0.2216   0.09204   0.08978  -0.0536   0.9606   0.0097
  -9.250  -0.1918   0.08842   0.08612  -0.0605   0.9484   0.0101
  -9.000  -0.1597   0.08402   0.08166  -0.0689   0.9307   0.0108
  -8.750  -0.1373   0.07783   0.07536  -0.0778   0.9024   0.0118
  -8.500  -0.1379   0.07188   0.06926  -0.0824   0.8646   0.0123
  -8.250  -0.1380   0.06900   0.06627  -0.0833   0.8363   0.0127
  -8.000  -0.1378   0.06690   0.06409  -0.0835   0.8145   0.0129
  -7.750  -0.1321   0.06469   0.06181  -0.0848   0.7954   0.0132
  -7.500  -0.1251   0.06203   0.05908  -0.0869   0.7774   0.0136
  -7.250  -0.1171   0.05897   0.05593  -0.0895   0.7590   0.0143
  -7.000  -0.1269   0.04584   0.04261  -0.1014   0.7437   0.0165
  -6.500  -0.1197   0.01921   0.01422  -0.1136   0.7190   0.0212
  -6.250  -0.0969   0.01815   0.01293  -0.1132   0.7036   0.0221
  -6.000  -0.0719   0.01790   0.01256  -0.1128   0.6880   0.0226
  -5.750  -0.0466   0.01766   0.01218  -0.1125   0.6743   0.0234
  -5.500  -0.0215   0.01718   0.01151  -0.1121   0.6637   0.0243
  -5.250   0.0039   0.01643   0.01054  -0.1118   0.6557   0.0253
  -4.750   0.0555   0.01512   0.00881  -0.1112   0.6437   0.0270
  -4.500   0.0819   0.01465   0.00817  -0.1110   0.6382   0.0275
  -4.250   0.1082   0.01420   0.00754  -0.1107   0.6332   0.0278
  -4.000   0.1336   0.01300   0.00610  -0.1104   0.6287   0.0289
  -3.750   0.1602   0.01251   0.00552  -0.1101   0.6242   0.0299
  -3.500   0.1868   0.01214   0.00505  -0.1099   0.6199   0.0305
  -3.250   0.2137   0.01180   0.00461  -0.1096   0.6157   0.0310
  -3.000   0.2408   0.01149   0.00423  -0.1094   0.6115   0.0316
  -2.750   0.2678   0.01121   0.00388  -0.1092   0.6075   0.0321
  -2.500   0.2947   0.01098   0.00357  -0.1089   0.6037   0.0326
  -2.250   0.3218   0.01074   0.00329  -0.1087   0.5997   0.0332
  -2.000   0.3490   0.01055   0.00306  -0.1085   0.5953   0.0342
  -1.750   0.3761   0.01039   0.00285  -0.1083   0.5912   0.0350
  -1.250   0.4306   0.01012   0.00250  -0.1078   0.5832   0.0363
  -1.000   0.4578   0.00999   0.00234  -0.1076   0.5784   0.0371
  -0.750   0.4848   0.00988   0.00219  -0.1074   0.5739   0.0392
  -0.500   0.5121   0.00980   0.00210  -0.1072   0.5696   0.0418
  -0.250   0.5394   0.00972   0.00204  -0.1070   0.5643   0.0451
   0.000   0.5663   0.00966   0.00200  -0.1068   0.5589   0.0546
   0.250   0.5934   0.00960   0.00198  -0.1066   0.5536   0.0730
   0.500   0.6205   0.00955   0.00197  -0.1064   0.5468   0.0894
   0.750   0.6471   0.00952   0.00197  -0.1062   0.5386   0.1082
   1.000   0.6736   0.00951   0.00197  -0.1059   0.5277   0.1277
   1.250   0.6997   0.00950   0.00199  -0.1055   0.5131   0.1543
   1.500   0.7255   0.00952   0.00201  -0.1052   0.4979   0.1846
   1.750   0.7513   0.00950   0.00207  -0.1048   0.4848   0.2315
   2.000   0.7722   0.00879   0.00223  -0.1039   0.4727   0.6132
   2.500   0.8406   0.00838   0.00243  -0.1067   0.4479   1.0000
   2.750   0.8656   0.00855   0.00253  -0.1061   0.4382   1.0000
   3.000   0.8910   0.00871   0.00263  -0.1057   0.4290   1.0000
   3.250   0.9162   0.00888   0.00274  -0.1052   0.4213   1.0000
   3.500   0.9417   0.00904   0.00286  -0.1047   0.4138   1.0000
   3.750   0.9668   0.00921   0.00300  -0.1042   0.4070   1.0000
   4.000   0.9923   0.00937   0.00313  -0.1038   0.4002   1.0000
   4.500   1.0427   0.00971   0.00344  -0.1029   0.3872   1.0000
   4.750   1.0676   0.00990   0.00361  -0.1024   0.3805   1.0000
   5.000   1.0927   0.01007   0.00378  -0.1020   0.3743   1.0000
   5.250   1.1174   0.01026   0.00396  -0.1015   0.3668   1.0000
   5.500   1.1418   0.01048   0.00417  -0.1010   0.3572   1.0000
   5.750   1.1652   0.01074   0.00438  -0.1003   0.3436   1.0000
   6.000   1.1887   0.01100   0.00461  -0.0996   0.3322   1.0000
   6.250   1.2115   0.01130   0.00486  -0.0988   0.3177   1.0000
   6.500   1.2326   0.01170   0.00517  -0.0978   0.2953   1.0000
   6.750   1.2518   0.01221   0.00555  -0.0965   0.2683   1.0000
   7.000   1.2706   0.01274   0.00595  -0.0951   0.2457   1.0000
   7.250   1.2890   0.01328   0.00639  -0.0937   0.2227   1.0000
   7.500   1.3064   0.01387   0.00688  -0.0922   0.2006   1.0000
   7.750   1.3156   0.01493   0.00763  -0.0894   0.1466   1.0000
   8.000   1.3254   0.01588   0.00840  -0.0867   0.1177   1.0000
   8.250   1.3380   0.01652   0.00900  -0.0843   0.1054   1.0000
   8.750   1.3513   0.01831   0.01055  -0.0779   0.0560   1.0000
   9.000   1.3552   0.01940   0.01157  -0.0746   0.0355   1.0000
   9.250   1.3573   0.02066   0.01274  -0.0712   0.0173   1.0000
   9.500   1.3663   0.02159   0.01370  -0.0689   0.0145   1.0000
   9.750   1.3768   0.02247   0.01465  -0.0670   0.0129   1.0000
  10.000   1.3871   0.02340   0.01566  -0.0651   0.0120   1.0000
  10.250   1.3964   0.02445   0.01679  -0.0633   0.0114   1.0000
  10.500   1.4035   0.02571   0.01814  -0.0614   0.0106   1.0000
  10.750   1.4093   0.02714   0.01966  -0.0597   0.0100   1.0000
  11.000   1.4141   0.02874   0.02134  -0.0580   0.0094   1.0000
  11.250   1.4207   0.03026   0.02295  -0.0566   0.0091   1.0000
  11.500   1.4272   0.03186   0.02463  -0.0554   0.0087   1.0000
  11.750   1.4323   0.03365   0.02651  -0.0543   0.0082   1.0000
  12.000   1.4361   0.03565   0.02859  -0.0533   0.0078   1.0000
  12.250   1.4389   0.03781   0.03084  -0.0524   0.0075   1.0000
  12.500   1.4405   0.04019   0.03332  -0.0516   0.0074   1.0000
  12.750   1.4402   0.04284   0.03607  -0.0510   0.0072   1.0000
  13.000   1.4355   0.04607   0.03939  -0.0505   0.0069   1.0000
  13.250   1.4318   0.04928   0.04271  -0.0501   0.0067   1.0000
  13.500   1.4311   0.05223   0.04576  -0.0498   0.0066   1.0000
  13.750   1.4296   0.05535   0.04899  -0.0498   0.0065   1.0000
  14.000   1.4271   0.05870   0.05244  -0.0498   0.0063   1.0000
  14.250   1.4236   0.06223   0.05608  -0.0500   0.0062   1.0000
  14.500   1.4217   0.06568   0.05963  -0.0503   0.0060   1.0000
  14.750   1.4172   0.06958   0.06363  -0.0508   0.0059   1.0000
  15.000   1.4137   0.07343   0.06759  -0.0514   0.0058   1.0000
  15.250   1.4099   0.07741   0.07167  -0.0521   0.0056   1.0000
  15.500   1.4068   0.08139   0.07574  -0.0530   0.0055   1.0000
  15.750   1.4052   0.08523   0.07968  -0.0539   0.0053   1.0000
  16.000   1.4013   0.08947   0.08401  -0.0550   0.0052   1.0000
  16.250   1.3976   0.09374   0.08836  -0.0562   0.0051   1.0000
  16.500   1.3929   0.09822   0.09294  -0.0575   0.0050   1.0000
  16.750   1.3877   0.10283   0.09764  -0.0589   0.0049   1.0000
  17.000   1.3816   0.10764   0.10253  -0.0605   0.0048   1.0000
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